Aeroplane



March 23, 1937. J. HJNOWSKI AEROPLANE Filed NOV. 30, 1954 5 Sheets-Sheet l March 23, 1937. 1 HOJNOWSKl 2,074,395

AEROPLANE Filed Nov. 30, 19134` 3 Sheets-Shegt 2 March-23, 1937. .1 HoJNowsKl I AEROPLANE s sheets-sheet 3 Filed Nov. 50, 1954 Patented Mar. 23, 1937 UNITED STATES PATENT OFFICE 2 Claims.

This invention relates to certain new and useful improvements in aeroplanes` An important object of the invention is to improve the motor drive of aeroplanes wherein the motor in the form of an internal combustion engine has an extended drive shaft carrying a multiple pulling block and laterally positioned driven shaft with a propeller blade on each driven shaft and belt drive connections between the pulley block and driven shaft for the lessening of driving noises incident to the operation of the propeller blades.

A further object of the invention is to provide an aeroplane wherein the wings are provided with 16 ailerons adapted for automatic operation when the aeroplane laterally tilts for bringing the same to an even keel by means of a transversely shiftable weight member gravitationally shifting in directions laterally of the aeroplane when the latter tilts to either side for the operation of the ailerons.

A further object of the invention is to provide stabilizing devices of the foregoing character wherein the ailerons are adapted to be operated by a pivotally suspended member functioning as a pendulum for restoring the aeroplane to an even keel when tilted laterally.

With the above and other objects in view that will become apparent as the nature of the invention is better understood, the same consists in the novel form, combination and arrangement of parts hereinafter more fully described, shown in the accompanying drawings and claimed.

In the drawings:-

Figure l is a top plan View, partly broken away of an aeroplane constructed in accordance with the present invention and showing the multiple belt drive from the motor shaft to the laterally positioned propeller shaft, the stabilizing ailerons carried by the wings and the operating means therefor;

Figure 2 is a fragmentary perspective View of the tank or weight shiftable laterally of the aeroplane for the operation of the ailerons for restoring the aeroplane to an even keel from laterally tilted positions;

Figure 3 is a side elevational view of another form of gearing interposed between the laterally shiftable weight and ailerons for increasing speed of movement of the latter when the aeroplane tilts laterally;

Figure 4 is a front elevational View of the aeroplane illustrated as laterally tilted with the ailerons in operative positions for restoring the 55 aeroplane to an even keel;

Figure 5 is a detail sectional view taken on line 5-5 of Figure 4;

Figure 6 is a side elevational view of the aeroplane, partly broken away and shown in section, illustrating the aeroplane in a downwardly tilted position with the ailerons shifted to a position for restoring the aeroplane to an even keel;

Figure 7 is a. top plan view of another form of aeroplane wherein the propeller blade is mounted directly on the motor shaft, the aeroplane being illustrated as tilted laterally and the ailerons shifted to operative position for restoring the aeroplane to an even keel;

Figure 8 is a diagrammatic top plan view of an aeroplane, similar to Figure 1, wherein the laterally positioned propeller shafts are housed within a casing;

Figure 9 is a fragmentary top plan view of an aeroplane, partly broken away and illustrating a pivotally suspended weight for the operation of ailerons for restoring the aeroplane to an even keel from laterally tilted positions; and

Figure 10 is a detail view of the aileron operating mechanism, shown in Figure 9.

Referring more in detail to the accompanying drawings and particularly to Figures 1 to 6, the reference numeral I5 designates the fuselage of an aeroplane provided with upper and lower wings I6 and Il respectively, an elevator I8 at its rear end and a motor l 9 at its forward end. The motor includes a drive shaft 2B upon which a multiple pulley block 2l is fixed.

The aeroplane is equipped with a pair of propeller blades 22 mounted on driven shafts 23 positioned laterally of the drive shaft 2D and the mounting for the driven shafts 23 is shown more clearly in Figures l, 4, and 5. Each shaft 23 is mounted in a pair of spaced supports 24 of channel formation in cross-section and of general U-shape, the outer end of each support 24 being closed as at 25. A bearing block 26 for the shaft 23 is shiftably mounted in the outer end of each support 24, being guided therein by the channel formation of the support and said blocks 26 are shiftable in the support by means of the adjusting screws 21 having a swivel connection 28 with the block 26 and threaded through the block 29 anchored in the inner end of the support 24, the screw 21 being operated by the handle 30. Each support carries an oil or grease cup 3| for the lubrication of the shaft 23. As shown more clearly in Figure l, a multiple pulley block 32 is carried by each shaft 23 in transverse alignment with the pulley block 2l on the motor shaft 2|] and said pulley blocks 2|] and 32 are connected by means of endless belts 33.

The belt drive between the motor shaft 20 and the laterally positioned propeller shaft 2| provides a single drive for the two propellers and also oper- 5 ates to lessen the noise incident to a gear drive and the driven shaft adjusting means provides proper tension on the drive belt 33 for the positive operation of the driven propeller shaft.

As shown in Figures 1 and 4, the trailing edges of the wings |6 and I1 are respectively provided with ailerons 34 and 35 connected by rods 36 for simultaneous operation and the operating means for said ailerons 34 and 35 is shown more clearly in Figures 1 and 2. A gas tank for the motor |9, l5 or a weight 31 is carried by a wheeled carriage 38 mounted on trackage 39 extending transversely of the fuselage |5 and the carriage 38 is provided with an upstanding fork 40 at one side thereof.

The shaft 4| extending longitudinally of the fuselage is journalled in bearings 42 and carries a crank arm 43 at one end cooperating with the fork 40 while the other end of the shaft 4| carries a bevelled gear 44. A shaft 45 is journalled longitudinally of each end of the wing |1 and to which the ailerons 35 are rigidly secured, a pinion 46 being secured to each adjacent end of the two shafts 45 for meshing engagement with the bevelled gear 44. It will therefore be seen that when the aeroplane tilts laterally, the gas tank or weight 31 will move over the trackage 39 and the fork of the carriage operates the crank arm 43 of the shaft 4| to rotate the bevel gear 44 and impart reverse rotation to the two shafts 45 to cause the ailerons 34 and 35 at each side of 35 the longitudinal axis of the aeroplane to be respectively raised or lowered as illustrated in Figure 4 for restoring the aeroplane to an even keel from a laterally tilted position.

A modified form of connecting means between 40 the laterally shiftable weight 31 and the aileron operating shaft 45 is shown in Figure 3, this connection operating to produce increased speed of movement to the ailerons relative to movement of the Weight. The shaft 4|a carries a crank 45 arm 43a adapted for engagement with the fork 40 of the wheeled carriage and said shaft 4|a carries a gear wheel 41 for meshing engagement with a pinion 48 on the shaft 49 that carries a bevel gear 44a that meshes with the pinions 46 50 of the shaft 45.

The forward and trailing edges of the wings I6 and |1 are provided with additional ailerons for bringing the aeroplane out of a nose dive and into even keel with operating means therefor and as shown in Figures 1 and 6, the leading edges of the wings I6 and I1 respectively carry downwardly moving ailerons 50 and 5|. while the trailing edges of the wings I6 and |1 respectively carry upwardly moving ailerons 52 and 53. A tank or weight 54 is shiftable longitudinally of the fuselage l5, being located adjacent the rear end thereof and being mounted on trackage 55 and said weight 54 carries laterally directed arms 56,

each having a link connection 51 with an arm 58 G5 projecting radially of a shaft 59 journalled in the lower wing I1 to which ailerons 53 are secured.

Arms 5|a and 52a respectively project from the pivot bearings of the ailerons 5| and 52 and are connected by a link. Ailerons 59 and 5| are oonnected by a link 6| while the ailerons 52 and 53 are connected by a link 62. It will therefore be seen that when the aeroplane enters a nose dive, the weight 54 will be shifted forwardly for the operation of the shaft 59 for simultaneously raising trailing ailerons 52 and 53 by their link oonnection 69 between the ailerons 52 and aileron 5|, the ailerons 56 and 5i simultaneously lowered.

The elevator i8 is automatically operated to aid in bringing the aeroplane out of a nose dive and as shown in Figures 1 and 6, a weighted receptacle or basket 53 is pivotally suspended from the upper end of the fuselage on a shaft B4 and has a link connection 65 with an arm 66 carried by the bearing for the elevator, rearward swinging movement of the weighted 'basket 63 being limited by the transversely extending abutment bar 61. As shown in Figure 6, the aeroplane is tilted downwardly and the basket 63 swung forwardly for the elevation of the rudder |8.

The aeroplane illustrated in Figure '1 is of the mono-plane type and the single propeller 68 is directly mounted on the shaft of the motor. The transversely shiftable Weight 31a carries a fork 49a while the ailerons 34d on the trailing edge of the Wings |6a each fits to a shaft 45a carrying a bevel pinion 48a at adjacent ends. The side connection between the weight 31a and shaft 45a is of the form illustrated in Figure 3 and includes the bevel gear 44a on the shaft 49 meshing with the bevel pinions 46a, the connection further including the pinion and gear combination 48 and 41. The aeroplane is illustrated in a laterally tilted position with the weight 31a laterally shifted for the operation of the shafts 45a and the ailerons 34a, one' aileron being lowered and the other one raised and operating to restore the aeroplane to an even keel toV bring the same out of the laterally tilted position.

In the diagrammatic showing in Figure 8, the nose end of the aeroplane 69 is provided with a housing 1U enclosing laterally positioned shafts for the dual propellers 22a and the belt drive with the motor shaft. This form of the invention embodies ailerons for restoring the aeroplane to an even keel out o-f laterally tilted positions and the operating mechanism for such ailerons 1| is shown more clearly in Figures 9 and l5. A shaft 12 is journalled longitudinally of the fuselage 69 and carries a weighted basket 13 adapted to swing laterally of the fuselage to effect reverse oscillations of the shaft 12, this arrangement being clearly shown in Figure 10. The shaft 12 carries a bevel gear 14 at its forward end that meshes with bevel pinions 15 xed to cross shafts 15 journalled longitudinally of each lateral wing spread and to which shaft 16 the ailerons 1| are Xed. It will be observed from an inspection of Figure 10 that when the weighted basket 13 swings laterally as indicated by dotted lines, the shafts 16 are reversely rotated for respectively raising or lowering the ailerons 1|.

From the above detailed description of the invention, it is believed that the construction and operation thereof will at once be apparent, and while there are herein shown and described the preferred embodiments of the invention, it is nevertheless to be understood that minor changes may be made therein without departing from the spirit and scope of the invention as claimed:

I claim:-

1. In a biplane of the character described, a fuselage, wings on the fuselage, ailerons carried by the leading and trailing edges of the wings for bringing the aeroplane out of a nose dive, link connections respectively between the ailerons at the leading and trailing edges of the wings, diagonal link connections between an aileron at the leading edge of a wing and an aile- CII ron at the trailing edge of the other wing, and a Weight slidable longitudinally of the fuselage and having link and arm connections with the ailerons at the trailing edge of one Wing for simultaneous operation of the ailerons.

2. In a biplane of the character described, a fuselage, wings on the fuselage, ailerons carried by the leading and trailing edges of the wings for bringing the biplane out of a nose dive, link 10 connections respectively between the ailerons at the leading and trailing edges of the wings, an arm extending angularly from an aileron at the leading edge of a wing, an arm extending angularly from an aileron at the trailing edge of the other wing, a link connection between said arms, and a Weight slidable longitudinally of the fuselage and having a link connection with the ailerons at the trailing edge of one wing for simultaneous operation of the ailerons. n

JAKOB HOJNOWSKI. 

